Abstract
The SiC fiber-reinforced SiC matrix composites are being evaluated for aircraft engine hot-section components dye to their low density, high strength, and fracture at elevated temperatures. The damage evolution and life prediction in 2D woven SiC/SiC composite have been investigated. The hysteresis loops models considering multiple matrix cracking modes have been used to establish the relationships between fatigue hysteresis loops, hysteresis dissipated energy, interface shear stress, and damage parameters. The effects of material properties, fatigue peak stress, matrix cracking, interface properties, and interface wear on fatigue hysteresis loops and interface slipping inside of ceramic-matrix composites (CMCs) have been analyzed. The damage evolution process under tension–tension fatigue loading has been analyzed using fatigue hysteresis dissipated energy, and the interface shear stress. The evolution of fatigue hysteresis dissipated energy, the interface shear stress and the broken fibers fraction versus cycle number, and the fatigue life S‒N curves of SiC/SiC at 1000, 1200, and 1300°C in air and steam conditions have been predicted.
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